System and method for inspecting turbomachines

ABSTRACT

A method for inspecting a turbomachine is provided. The method includes the steps of, attaching a gimbal mount to the turbomachine, inserting a probe into the turbomachine through the gimbal mount, and adjusting a position of the probe via the gimbal mount. A removing step removes the probe from the turbomachine. An attaching step attaches a traverse actuator system to the gimbal mount. The traverse actuator system is connected to the gimbal mount through a pressure isolation system. A reinserting step is used to reinsert the probe back into the turbomachine. An inspecting step is used to inspect or test the turbomachine.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to turbomachine inspectionand/or testing. More particularly, the subject matter relates to asystem and method for inspecting and/or testing operating turbomachines.

In a turbine system, such as a steam turbine system, fluid flow isdirected to selected portions of the turbine system to enable productionof mechanical energy. Parameters relating to the fluid flow in thesystem may be measured to evaluate efficiency and performance for aparticular turbine design. For example, pressure may be tested atselected locations in the turbine system using pressure tap assemblies.In certain locations, space for installation of the pressure tapassembly is reduced, causing difficulties when attempting to properlyseal the assembly in the component. Fluid leaks at the pressure tapassembly proximate the main flow path can disrupt fluid flow, lead tomeasurement errors and reduce the accuracy of turbine efficiencycalculations. Pressure tap assemblies are fixed and are limited toreadings at a single location. Therefore, samples are difficult, if notimpossible, to obtain from multiple locations in the operating steamturbine.

BRIEF DESCRIPTION OF THE INVENTION

In an aspect of the present invention, a method for inspecting aturbomachine is provided. The method includes the steps of, attaching agimbal mount to the turbomachine, inserting a probe into theturbomachine through the gimbal mount, and adjusting a position of theprobe via the gimbal mount. A removing step removes the probe from theturbomachine. An attaching step attaches a traverse actuator system tothe gimbal mount. The traverse actuator system is connected to thegimbal mount through a pressure isolation system. A reinserting step isused to reinsert the probe back into the turbomachine. An inspectingstep is used to inspect or test the turbomachine.

In another aspect of the present invention, a method for inspecting anoperating turbomachine is provided. The method includes the step ofattaching a gimbal mount to the turbomachine. The gimbal mount includesa plurality of turnbuckles located at equal intervals around the gimbalmount, and the gimbal mount is configured to be mounted to a port or avessel flange of the turbomachine. Adjustment of the turnbucklestranslates into a tangential or axial adjustment of a sensor headposition for the probe. An inserting step inserts a probe into theturbomachine through the gimbal mount. An adjusting step adjusts aposition of the probe via the gimbal mount. A removing step removes theprobe from the turbomachine. An attaching step attaches a traverseactuator system to the gimbal mount. The traverse actuator system isconnected to the gimbal mount through a pressure isolation system. Aconnecting step connects a mounting plate to a complementary mountingplate. The mounting plate is attached to a rail, and the rail supportsboth the pressure isolation system and the gimbal mount. The mountingplate is configured to align with the complementary mounting plateconnected to the traverse actuator system, and a plurality of keys areinterposed between the mounting plate and the complementary mountingplate to ensure alignment between the traverse actuator system and thegimbal mount. A reinserting step reinserts the probe back into theturbomachine. An inspecting step inspects and/or tests the turbomachine,and a reading step reads at least one of pressure values, temperaturevalues or moisture values obtained from within the operatingturbomachine.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a simplified schematic illustration of a combined cycle powerplant.

FIG. 2 illustrates a perspective view of a system for inspecting aturbomachine, according to an aspect of the present invention.

FIG. 3 illustrates a side view of a system for inspecting aturbomachine, according to an aspect of the present invention.

FIG. 4 illustrates a perspective view of the pressure isolation systemand the gimbal mount, according to an aspect of the present invention.

FIG. 5 illustrates a cross-sectional view of the pressure isolationsystem and gimbal mount, according to an aspect of the presentinvention.

FIG. 6 illustrates a schematic diagram of a system that may be used toinspect a turbomachine, according to an aspect of the present invention.

FIG. 7 illustrates a flowchart of a method for inspecting aturbomachine, according to an aspect of the present invention.

FIG. 8 illustrates a partial side view of the sensor head, according toan aspect of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

One or more specific aspects/embodiments of the present invention willbe described below. In an effort to provide a concise description ofthese aspects/embodiments, all features of an actual implementation maynot be described in the specification. It should be appreciated that inthe development of any such actual implementation, as in any engineeringor design project, numerous implementation-specific decisions must bemade to achieve the developers' specific goals, such as compliance withmachine-related, system-related and business-related constraints, whichmay vary from one implementation to another. Moreover, it should beappreciated that such a development effort might be complex and timeconsuming, but would nevertheless be a routine undertaking of design,fabrication, and manufacture for those of ordinary skill having thebenefit of this disclosure.

When introducing elements of various embodiments of the presentinvention, the articles “a,” “an,” “the,” and “said” are intended tomean that there are one or more of the elements. The terms “comprising,”“including,” and “having” are intended to be inclusive and mean thatthere may be additional elements other than the listed elements. Anyexamples of operating parameters and/or environmental conditions are notexclusive of other parameters/conditions of the disclosed embodiments.Additionally, it should be understood that references to “oneembodiment”, “one aspect” or “an embodiment” or “an aspect” of thepresent invention are not intended to be interpreted as excluding theexistence of additional embodiments or aspects that also incorporate therecited features.

FIG. 1 is a simplified schematic illustration of a combined cycle powerplant 100. The power plant 100 includes a steam turbine 110, a generator120 a gas turbine 130 and a heat recovery steam generator (HRSG) 140.The steam turbine 110 is connected to the generator via shaft 152 and aclutch (not shown). The generator is connected to the gas turbine viashaft 154. The exhaust of gas turbine 130 is connected to HSRG 140 viaduct 156, or in some applications the HSRG 140 may either be directlyconnected to the exhaust of turbine 130 or connected to the exhaustthrough a diffuser (not shown). The steam turbine 110 converts thethermal energy in steam to rotational movement. Steam strikes the bladesof the steam turbine, causing the steam turbine rotor shaft to rotate.The rotating shaft drives the generator 120. The gas turbine 130, whichincludes a compressor 131 and a turbine section 132, compresses air andmixes it with fuel. The fuel is burned and the hot air-fuel mixture isexpanded through the gas turbine blades, making them spin. The spinninggas turbine shaft drives the generator 120, which converts the spinningenergy into electricity. The HSRG 140 turns the gas turbine exhaust heatinto steam, and this steam is then fed into steam turbine 110.

The steam turbine 110, compressor 131 and gas turbine 132 are allturbomachines. Turbomachines may include multiple stages of blades,buckets, nozzles and vanes. The blades and buckets are rotating elementsincluding airfoil sections. The airfoil sections are designed for highefficiency. At times, it is desirable to inspect and/or test theoperation of turbomachines to either (1) validate predicted operatingparameters and conditions, or (2) identify problem locations orcomponents, or operating conditions causing undesired characteristics.In some cases, it may be helpful to monitor pressure or temperaturealong multiple radial distances near a blade. For example, one readingcould be taken near the rotor shaft, a second reading near a blade tipand a third reading near the middle of the blade. In the past this hasbeen very difficult, if not impossible, because one could not easily,safely and accurately move a probe in an operating turbomachine. Theturbomachine has to be operating for accurate operating measurements.Unfortunately, the blades rotate circumferentially at high speeds andthe machines may be under vacuum or pressure, and this makes moving aprobe and maintaining the machine seals problematic.

FIG. 2 illustrates a perspective view of a system 200 for inspecting aturbomachine, and FIG. 3 illustrates a side view of a system forinspecting a turbomachine, according to an aspect of the presentinvention. The system 200 includes a traverse actuator system 210,pressure isolation system 220 and a gimbal mount 230. The pressureisolation system 220 is connected to the traverse actuator 210, and isconfigured to maintain a pressure resistant seal around the probe 212.The gimbal mount 230 is connected to the pressure isolation system 220.The probe 212 may be formed of an elongated shaft with a sensor head 213at one end and a plurality of output ports 214 located at an opposingend of the shaft. As one example, the sensor head 213 may be a S-portpressure sensor, and accordingly there would be five output ports 214 atan opposing end of the elongated shaft. Alternatively, the sensor head213 could be a temperature sensor, a moisture or humidity sensor, or acamera or any other desired sensor device. The elongated shaft of probe212 is sized for the specific turbine or turbomachine. Any suitablelength may be employed, as long as the probe can travel the desireddistance into the turbomachine.

The system 200 is configured to mount onto the outer shell or casing ofthe turbomachine, so that the probe 212 will be aligned to an accessport therein. In the example shown, the system 200 is mounted to thesteam turbine's 110 casing. An access port 111 is located in the casingof the steam turbine and the probe 212 passes through this opening. Thegimbal mount 230 may be fastened to the port 111 by mechanicalfasteners, clamps or any other suitable attachment means. A pair ofleveling feet 231 may be used to balance and steady the system againstthe casing of the steam turbine 110.

The traverse actuator 210 includes a carriage 240 configured to move theprobe 212 in a linear or radial direction (with respect to theturbomachine) into and out of the turbomachine. A track 215 has aplurality of linearly arranged teeth 217 configured for operation withthe carriage 240. The teeth may be located on one or both sides of thetrack. A motor 260 is operably connected with the carriage 240 and track215, and is configured to engage the teeth of the track so thatoperation of the motor forces the carriage to move along the track. Forexample, the motor may be connected to a gearbox and/or a roller pinionthat engages the track teeth. When the roller pinion is rotated by themotor, the carriage 240 moves along the track 215, and the probe movestoward or away from the steam turbine 110. As FIG. 2 illustrates, thecarriage 240 is at its most forward position indicating that the probeis at the deepest position within steam turbine 110. The motor can beenergized to move carriage back along track 215 to withdraw the probe'ssensor head 213.

The traverse actuator 210 also includes an enclosure 250 that isconfigured to operate in hazardous environments. For example, a hydrogenexclusion zone could be considered a hazardous environment, or anyturbomachine that operates under a pressure or vacuum may presenthazardous conditions. The enclosure 250 may contain motor 260, sensorsfor reading the outputs 214 of probe 212, and/or any other desiredinspection equipment. The traverse actuator may also include a yaw drive216 configured to rotate the probe about the radial axis. The yaw drivecan include a motor and one or more rollers that engage the probe 212.If the sensor head 213 needs to be rotated, then the yaw drive canadjust the rotational position of the sensor head 213 (e.g., by about+/−180 degrees, +/−150 degrees, etc.). A camera 270 is mounted to thetraverse actuator and is configured to observe an insertion location ofthe probe 212. The camera 270 is ruggedized and configured to operate inhazardous environments (e.g., it can be explosion resistant). The cameraenables an operator to remotely view the system 200 and the insertionlocation of steam turbine 110, from a safe and secure location. Thecamera can be mounted on an extending arm 272 for an elevated worksiteview. In addition, the camera 270 can be connected to the remotemonitoring station (that has a display) via a wired or wireless link.The camera can be configured to pan or zoom to a specific field of view,all under remote control.

A leg assembly 280 (e.g., a bipod, tripod, etc.) may also be attached totraverse actuator 210 to stabilize and secure the system. The legassembly 280 includes a plurality of adjustable length legs configuredto lock in position at a desired length. For example, two main legs 281may be telescopic and have fasteners (e.g., bolts) to lock each leg at adesired length. A third leg 282 may slide within a clamp that also locksthe third leg in a desired position and length (e.g., via a clamp). Thetraverse actuator 210 may also include an articulated cable guide 360comprised of a plurality of chain links 362. The articulated cable guide360 retains a plurality of cables that may extend between the outputports 214 and the enclosure 250. The cable guide 360 is comprised of twospaced but parallel chain link walls 362, and a segmented floor 364. Thecables reside between the walls 362 and may be retained by top members366. The cable guide 360 follows (e.g., bends and flexes with) themovement of the carriage 240 so that the cables avoid catching onobstructions as the carriage moves back and forth along rail 303.

FIG. 4 illustrates a perspective view of the pressure isolation system220 and gimbal mount 230, according to an aspect of the presentinvention. FIG. 4 illustrates a cross-sectional view of the pressureisolation system 220 and gimbal mount 230, according to an aspect of thepresent invention. The pressure isolation system 220 is mounted ontorail 301, which in turn is connected to leveling feet 231 (only one ofwhich is shown). The probe 212 is shown inserted into the pressureisolation system. A probe bearing 310 facilitates movement of the probe212, and the bearing 310 could be comprised of roller bearings, ballbearings or any other suitable low friction device or material. Forexample, as the probe 212 is moved back and forth (or along a radialaxis of the turbomachine) the bearing 310 reduces friction between theprobe 210 and the surrounding components of the system. A pressure sealblock 320 isolates the pressure within the turbomachine from theexternal atmosphere, and seals along the outer circumference of probe212. The pressure seal block 320 may be connected to a pressurized orvacuum source. For example, if the turbomachine location undergoinginspection is at 10 psi, the seal block could be maintained at about 15psi to prevent undesired leakage.

A valve seal 330 is located between the gimbal mount 230 and thepressure seal block 320. The valve seal 330 is configured to isolate thepressure seal block 320 from the gimbal mount 230 when the probe is notin the valve seal. In addition, the valve seal 330 can be closed toisolate the internal working area of the turbomachine from the externalatmosphere. The valve seal may be a ball valve seal (as shown), aguillotine seal or any other suitable seal.

The gimbal mount 230 mounts to the port flange on the turbomachine'scasing. For example, the gimbal mount may be mounted to the port orvessel flange with the use of bolts and nuts. The leveling feet 231 maythen be adjusted until they contact the vessel or casing. The gimbalmount is configured to permit radial and axial adjustment of the probe'slocation. When the probe 212 is inserted in the turbomachine the sensorhead 213 may be too near or too far away from a blade, or it may be toonear or too far away from the rotor shaft. Four turnbuckles 340 arelocated at 90 degree intervals around the gimbal mount. In FIG. 4, thetop (i.e., 0 degree) and side (270 degree) turnbuckles are shown, and inFIG. 5 only the top (0 degree) and bottom (90 degree) turnbuckles areshown. To adjust the axial position of sensor head 213, the side (firstset of) turnbuckles can be adjusted. For example, the 90 degreeturnbuckle can be tightened and the 270 degree turnbuckle can beloosened to move the sensor head 213 in the axial direction. To adjustthe sensor head in the tangential direction, the 0 degree and 180 degree(second set of) turnbuckles can be respectively tightened and loosened.This adjustability is extremely helpful as the port flanges are notalways manufactured to close tolerances and many (if not all) were neverdesigned to be used with highly accurate inspection equipment, such asthe present invention. This adjustability also permits the operator toalign the probe 212 so that the probe 212 or sensor head 213 do notcontact undesired rotating parts of the turbomachine.

The gimbal mount 230 and pressure isolation system 220 may be attachedto the traverse actuator system via mounting plate 350, which isattached to rail 301. The traverse actuator system includes acomplementary mounting plate 302 (attached to rail 303) and the keys 351ensure proper alignment between the traverse actuator system and thepressure isolation system/gimbal mount. The keys 351, which may beattached to either mounting plate, are interposed between the mountingplate 350 and the complementary mounting plate 302. As can be seen, thekeys 351 ensure proper alignment between the traverse actuator system210 and the pressure isolation system 220 and gimbal mount 230.

FIG. 6 illustrates a schematic diagram of a system 500 that may be usedto inspect a turbomachine, according to an aspect of the presentinvention. The system 500 includes the traverse actuator 210, pressureisolation system 220 and gimbal mount 230, generally indicated by 501.Four of these systems 501 are distributed around, and are attached to,the turbomachine 110. However, only the cabling and communication linksare shown for one system, for clarity. Each system 501 can inspect adifferent part or stage of the turbomachine. The turbomachine 110 (e.g.,a steam turbine) is located in a hazardous area (located to the right ofline 505), and a safe area (located to the left of line 505) is locatedaway from the steam turbine 110. The hazardous area may be the areadirectly around the turbomachine, or a room enclosing the turbomachine.The safe area may be located either a safe distance away from theturbomachine, in a different room or in a remote monitoring station. Thesystem control computer 510 and camera control computer 520 are bothlocated in the safe area. Both the system control computer 510 and thecamera control computer may be connected to the enclosure 250 andmonitoring station/display 530 by a wired or wireless link. For example,ethernet cables 512 may be employed as a communication link. However,any suitable wired or wireless (e.g., radio frequency, wifi, Bluetooth,etc.) communication link may be employed. In some applications, thesystem control computer 510 and camera control computer 520 may becombined into a single device. The system control computer 510 or thecamera control computer 520 may function as a monitoring station havinga display, or the monitoring station/display 530 may be a separatedevice or located remotely from the system 501 or system 500.

The controller 513 may also include power inputs 514 (e.g., 90-240 voltsAC) for powering electrical devices, and a pressurized gas input 516 forsupplying pressurized gas to the pressure seal block 320 via gas output517. For example, pressurized air at about 60 PSI may be supplied toseal block 320 via gas output 517. A plurality of motor and feedbackcables 518 extend between the controller 513 and enclosure 250. Withthis arrangement and configuration, a remotely located operator (in thesafe area) can monitor and control the inspection process. The cameras270 may be controlled (e.g., panned, zoomed focused, etc.) by cameracontrol 520. The system 501 and probe 212 can be controlled with systemcontrol computer 510. The system control computer may also include adisplay for viewing images from cameras 270. The system control computer510 also includes a human machine interface (HMI) for controlling theprobe 212. For example, linear (i.e., radial) movement of the probe iscontrolled as well as activation of motor 260, and rotation (i.e.,yawing) of the probe 212 by yaw drive 216 is controlled. The systemcontrol computer 510 may also display PSI readings, warnings/alarms,temperatures, and any other data that may be of interest during theinspection and/or testing process.

FIG. 7 illustrates a flowchart of a method 600 for inspecting aturbomachine, according to an aspect of the present invention In step610, the gimbal mount 230 is attached to the vessel flange of theturbomachine with mechanical fasteners. The leveling feet 231 areadjusted until they contact the vessel (the vessel is the turbomachinecasing), and may be locked in place with lock nuts. In step 620, a probeor camera may be inserted into the turbomachine through the gimbalmount. In step 630, the position of the probe is adjusted with thegimbal mount's turnbuckles 340. Once the desired probe position andorientation is obtained the turnbuckles may be locked in place with jamnuts. In step 640, the probe may be removed from the turbomachine andgimbal mount 230. In step 650, the traverse actuator 210 is attached tothe gimbal mount 230 and pressure isolation system 220 via mountingplates 350, 302. The alignment keys 351 ensure correct probe alignmentbetween the pressure isolation system and the traverse actuator.Mechanical fasteners may be used to attach the traverse actuator to themounting plate 350. The traverse actuator system is also connected tothe gimbal mount through or via the pressure isolation system. The legassembly may now be deployed and adjusted to the desired height. Thelegs of the leg assembly may be telescoping to allow for easy heightadjustment. In step 660, the probe 212 is re-inserted into theturbomachine through the pressure isolation system and gimbal mount. Instep 670, the system is activated to insert the probe into the machineto begin the inspection and/or testing and take readings of variousparameters (e.g., pressure, temperature, moisture, etc.).

FIG. 8 illustrates a partial side view of the sensor head 213, accordingto an aspect of the present invention. The sensor head 213 may comprisea pressure probe 800 that has a plurality of ports 801-803. The ports801-803 may be pressure sensing ports and the sensor head may includeone to seven or more pressure sensing ports. Multiple ports allow fordifferential pressure sensing capabilities, and the multiple ports maybe evenly or unevenly distributed around the distal end of probe 800.For example, the pressure at a specific location (e.g., between specificstages, or at specific radial or axial locations) in the turbomachinemay be desired and the probe 800 can detect this pressure. The probe 800may also include a moisture probe/port 810 and a temperature probe/port820. Alternatively, the entire probe 800 may be configured as a moistureor temperature probe. The probe 800 may also include a camera 830 orimaging device. For example, the camera 830 can aid in verifyingaccurate probe placement or in identification of foreign objects/debrisor damage.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they have structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal languages of the claims.

1. A method for inspecting a turbomachine, the method comprising thesteps of: attaching a gimbal mount to the turbomachine; inserting aprobe into the turbomachine through the gimbal mount; adjusting aposition of the probe via the gimbal mount; removing the probe from theturbomachine; attaching a traverse actuator system to the gimbal mount,the traverse actuator system is connected to the gimbal mount through apressure isolation system; reinserting the probe back into theturbomachine; and inspecting or testing the turbomachine.
 2. The methodof claim 1, wherein the gimbal mount further comprises: a plurality ofturnbuckles located at equal intervals around the gimbal mount; andwherein the gimbal mount is configured to be mounted to a port or avessel flange of the turbomachine, and adjustment of the turnbucklestranslates into a tangential or axial adjustment of a sensor headposition for the probe.
 3. The method of claim 2, wherein there are fourturnbuckles located at 90 degree intervals around the gimbal mount, theadjusting a position of the probe step further comprising: adjusting afirst set of turnbuckles spaced by 180 degrees to move the probe in anaxial direction with respect to the turbomachine, and adjusting a secondset of turnbuckles spaced by 180 degrees to move the probe in atangential direction with respect to the turbomachine; wherein the firstset of turnbuckles is 90 degrees offset from the second set ofturnbuckles.
 4. The method of claim 2, the attaching a traverse actuatorsystem step further comprising: connecting a mounting plate to acomplementary mounting plate, the mounting plate is attached to a rail,and the rail supports both the pressure isolation system and the gimbalmount, the mounting plate is configured to align with the complementarymounting plate connected to the traverse actuator system; and wherein aplurality of keys are interposed between the mounting plate and thecomplementary mounting plate to ensure alignment between the traverseactuator system and the gimbal mount.
 5. The method of claim 1, whereinthe inspecting step further comprises: reading at least one of pressurevalues, temperature values or moisture values obtained from within theoperating turbomachine.
 6. The method of claim 1, the probe furthercomprising at least one of: a pressure probe having a plurality ofports, a moisture probe, a temperature probe, a camera.
 7. The method ofclaim 1, the probe further comprising: a pressure probe having aplurality of ports, and an elongated shaft having a sensor head locatedat one end and a plurality of output ports located at an opposing end ofthe elongated shaft.
 8. The method of claim 1, the pressure isolationsystem further comprising: a valve seal located between the gimbal mountand a pressure seal, the valve seal configured to isolate the pressureseal from the gimbal mount when the probe is not in the valve seal; anda probe bearing located adjacent to the pressure seal, the probe bearingconfigured to facilitate back and forth movement of the probe byreducing friction.
 9. The method of claim 8, wherein the valve seal isat least one of: a ball valve seal or a guillotine seal.
 10. The methodof claim 8, wherein the probe bearing is comprised of at least one of:roller bearings, ball bearings, or low friction material.
 11. The methodof claim 8, further comprising the step of: connecting the pressure sealto a pressurized source or a vacuum source.
 12. The method of claim 1,the traverse actuator system further comprising: a carriage configuredto move the probe into and out of the turbomachine; a track having aplurality of linearly arranged teeth, the track configured for operationwith the carriage; and a motor operably connected with the carriage andtrack, the motor configured to engage the plurality of linearly arrangedteeth so that operation of the motor forces the carriage to move alongthe track.
 13. The method of claim 12, the traverse actuator systemfurther comprising: an enclosure configured to operate in hazardousenvironments, the enclosure housing the motor; and a yaw driveconfigured to rotate the probe about a radial axis of the turbomachine.14. The method of claim 12, the traverse actuator system furthercomprising: monitoring an insertion location of the probe with a camera,the camera configured to operate in hazardous environments; and whereinthe camera is connected to a monitoring station having a display. 15.The method of claim 12, the traverse actuator system further comprising:a leg assembly attached to a rail of the traverse actuator system, theleg assembly configured to stabilize the traverse actuator system, theleg assembly having a plurality of adjustable length legs configured tolock in position at a desired length.
 16. The method of claim 12, thetraverse actuator system further comprising: an articulated cable guidecomprised of a plurality of chain links, the articulated cable guideconfigured to retain a plurality of cables, and to follow movement ofthe carriage so that the cables avoid catching on obstructions.
 17. Amethod for inspecting an operating turbomachine, the method comprisingthe steps of: attaching a gimbal mount to the turbomachine, the gimbalmount comprising a plurality of turnbuckles located at equal intervalsaround the gimbal mount, and wherein the gimbal mount is configured tobe mounted to a port or a vessel flange of the turbomachine, andadjustment of the turnbuckles translates into a tangential or axialadjustment of a sensor head position for the probe; inserting a probeinto the turbomachine through the gimbal mount; adjusting a position ofthe probe via the gimbal mount; removing the probe from theturbomachine; attaching a traverse actuator system to the gimbal mount,the traverse actuator system is connected to the gimbal mount through apressure isolation system, connecting a mounting plate to acomplementary mounting plate, the mounting plate is attached to a rail,and the rail supports both the pressure isolation system and the gimbalmount, the mounting plate is configured to align with the complementarymounting plate connected to the traverse actuator system, a plurality ofkeys are interposed between the mounting plate and the complementarymounting plate to ensure alignment between the traverse actuator systemand the gimbal mount; reinserting the probe back into the turbomachine;and inspecting or testing the turbomachine, and reading at least one ofpressure values, temperature values or moisture values obtained fromwithin the operating turbomachine.
 18. The method of claim 17, the probefurther comprising at least one of: a pressure probe having a pluralityof ports, a moisture probe, a temperature probe, a camera, or anelongated shaft having a sensor head located at one end and a pluralityof output ports located at an opposing end of the elongated shaft. 19.The method of claim 18, the pressure isolation system furthercomprising: a valve seal located between the gimbal mount and a pressureseal, the valve seal configured to isolate the pressure seal from thegimbal mount when the probe is not in the valve seal; and a probebearing located adjacent to the pressure seal, the probe bearingconfigured to facilitate back and forth movement of the probe byreducing friction, the probe bearing comprised of at least one of,roller bearings, ball bearings, or low friction material.
 20. The methodof claim 19, the traverse actuator system further comprising: a carriageconfigured to move the probe into and out of the turbomachine; a trackhaving a plurality of linearly arranged teeth, the track configured foroperation with the carriage; a motor operably connected with thecarriage and track, the motor configured to engage the plurality oflinearly arranged teeth so that operation of the motor forces thecarriage to move along the track; an enclosure configured to operate inhazardous environments, the enclosure housing the motor; a yaw driveconfigured to rotate the probe about a radial axis of the turbomachine;and an articulated cable guide comprised of a plurality of chain links,the articulated cable guide configured to retain a plurality of cables,and to follow movement of the carriage so that the cables avoid catchingon obstructions.